Quick connecting device for wing body of aircraft

Abstract

The invention discloses a quick connecting device for an aircraft wing body. Two ends of at least one guide rod are respectively connected to adjacent beams in the airfoil; the first butt joint seat and the second butt joint seat are slidably connected to the two sides of the guide rod correspondingly and located on the inner sides of the adjacent beams in the airfoil; locking holes are formed in the first butt joint seat and the second butt joint seat; one end of each of at least two locking mechanisms penetrates through the corresponding locking hole and extends into the corresponding first butt joint seat and the second butt joint seat; a limiting frame of the machine body is provided with a limiting hole corresponding to the locking hole; the two ends of the first stretching piece stretch into the first butt joint base and the second butt joint base correspondingly and are connected to the corresponding locking mechanisms. The two ends of the second stretching piece are connected to the first butt joint base and the second butt joint base correspondingly. The latch hook mechanism is connected to the first stretching piece and the second stretching piece. The first stretching piece and the second stretching piece are pulled through the rapid action of the lock hook mechanism, stretching-in and withdrawing of the locking mechanism are achieved, and the connecting and detaching time of the wing body is shortened.

Description

Technical Field

[0001] The present application relates to the field of aircraft technology, and in particular to an aircraft wing-body quick connection device. Background Art

[0002] Aircraft are unmanned aircraft that are controlled by radio remote control equipment and self-contained program control devices. They are usually equipped with various advanced technical equipment such as autopilots and program control devices. Ground operators can track, locate, remotely control, telemeter and transmit digital information to aircraft through radar, positioning systems and other equipment. Therefore, aircraft have been widely used in many fields such as aerial reconnaissance, surveillance, communication, anti-submarine, and electronic jamming.

[0003] For detachable aircraft, the fuselage, wings and tail can be disassembled, which is convenient for storage and transportation. At present, the wings or tail are mostly connected to the fuselage by bolts. However, this connection method not only requires sufficient space to complete the installation and removal of the bolts, thus occupying a relatively large space, but also the installation and removal of the bolts requires manual operation, which is time-consuming and physically demanding. Summary of the invention

[0004] The embodiment of the present application provides an aircraft wing-fuselage quick connection device, which solves the technical problems in the prior art that the wing or tail of an aircraft is connected to the fuselage by bolts, which requires sufficient space to be reserved for installation workers to install and remove the bolts, occupies a large space, and the removal of the bolts is time-consuming and labor-intensive.

[0005] The embodiment of the present application provides an aircraft wing-body quick connection device, comprising a first docking seat, a second docking seat, a locking hook mechanism, a first stretching member, a second stretching member, at least one guide rod and at least two locking mechanisms; at least one of the two ends of the guide rod is respectively connected to adjacent beams in the wing surface; the first docking seat and the second docking seat are respectively slidably connected to the two sides of the guide rod, and are located on the inner side of the adjacent beams in the wing surface, and are configured to be inserted into the corresponding limit frame of the fuselage; the first docking seat and the second docking seat are both provided with locking holes; one end of at least two of the locking mechanisms passes through the corresponding locking holes and extends into the corresponding first docking seat and the second docking seat; The limiting frame of the fuselage is provided with a limiting hole corresponding to the locking hole; the two ends of the first stretching member respectively extend into the first docking seat and the second docking seat, and are connected to the corresponding locking mechanism; the two ends of the second stretching member are respectively connected to the first docking seat and the second docking seat; the locking hook mechanism is connected to the first stretching member and the second stretching member, and is configured to pull the first stretching member and the second stretching member so that the first stretching member drives the locking mechanism located outside the locking hole to extend into the corresponding first docking seat and the second docking seat, and at the same time, the second stretching member drives the first docking seat and the second docking seat to move in a direction close to each other.

[0006] In a possible implementation, the first stretching member includes a rope, two reset elastic members and two baffles; the two reset elastic members and the two baffles are respectively located in the first docking seat and the second docking seat; the two ends of the rope extend into the first docking seat and the second docking seat respectively, and pass through the corresponding baffles to be connected to the corresponding locking mechanism; one end of the two reset elastic members is fixed to the side of the corresponding baffle facing the locking mechanism, and the other end thereof is abutted against the corresponding locking mechanism.

[0007] In one possible implementation, the aircraft wing-body quick connection device also includes two support guide seats; the two support guide seats are respectively fixedly connected to the first docking seat and the second docking seat, and are located on the side of the baffle away from the locking mechanism; after the two ends of the rope extend into the first docking seat and the second docking seat, they bypass the corresponding support guide seats, and the support guide seats are configured to guide the rope through the corresponding baffle.

[0008] In a possible implementation, the locking mechanism includes a slider, a tension spring and two locking pins; the slider and the tension spring are both provided in the first docking seat and the second docking seat; the two ends of the first tensile member are respectively connected to the corresponding slider; the slider is a hollow structure; the two ends of the tension spring respectively pass through the top wall and the bottom wall of the slider and are connected to the two locking pins, and the two sides of the tension spring abut against the top wall and the bottom wall of the slider; the longitudinal section of the slider away from the first tensile member is a triangular structure; one end portion of the two locking pins away from the tension spring extends out of the corresponding locking hole, and the side of the two locking pins close to the tension spring is slidably connected to the top surface and the bottom surface of the slider away from the first tensile member.

[0009] In a possible implementation, the locking mechanism also includes a guide column; the two locking pins are slidably connected to both sides of the guide column; the tension spring is sleeved on the outer wall of the guide column; and the top surface and bottom surface of the sliding block on the side away from the first tensile member are both provided with sliding grooves corresponding to the guide column.

[0010] In a possible implementation, the aircraft wing-body quick connection device also includes at least one compression spring; at least one of the compression springs is disposed between the first docking socket and the second docking socket and is configured to limit the distance between the first docking socket and the second docking socket.

[0011] In a possible implementation, the lock hook mechanism includes a first lock shell, a second lock shell, a limit seat, a draw button lock hook and a connecting rod; the first lock shell is arranged on the skin of the fuselage; the second lock shell is arranged on the skin of the wing surface and corresponds to the first lock shell; the first lock shell and the second lock shell are located between the first docking seat and the second docking seat; the limit seat is arranged on the first lock shell; a through hole is arranged on the side of the second lock shell away from the first lock shell, and one end of the connecting rod passes through the through hole; the connecting rod is provided with connecting holes for the first stretching member and the second stretching member to pass through at intervals along its height direction; one end of the draw button lock hook is rotatably connected to the side of the connecting rod away from the connecting hole, and is configured to pull the connecting rod to move when the angle with the second lock shell is 90°; the other end of the draw button lock hook is a free end, which is configured to be inserted into the limit seat.

[0012] In a possible implementation, the buckle lock hook is made of hard rubber; the limiting seat is a U-shaped structure, and the top opening width of the U-shaped structure is smaller than the bottom opening width.

[0013] In a possible implementation, the lock hook mechanism also includes a lock cover; the lock cover is hinged to one end of the second lock shell away from the first lock shell, and a spring latch is provided on the side of the lock cover away from the second lock shell; and a pin seat corresponding to the spring latch is provided on the side of the second lock shell away from the first lock shell.

[0014] In a possible implementation, the longitudinal sections of the first docking seat and the second docking seat are both first trapezoidal structures; and the longitudinal section of the limiting frame of the fuselage is a second trapezoidal structure corresponding to the first trapezoidal structure.

[0015] One or more technical solutions provided in the embodiments of the present application have at least the following technical effects: The aircraft wing-body quick connection device provided in the embodiment of the present application comprises a first docking seat, a second docking seat, a locking hook mechanism, a first stretching member, a second stretching member, at least one guide rod and at least two locking mechanisms. When the wing-body needs to be connected, the locking hook mechanism is activated and starts to pull the first stretching member and the second stretching member. As the first stretching member moves, it drives the locking mechanism originally located outside the locking hole to extend into the corresponding first docking seat and the second docking seat. At the same time, the second stretching member is pulled, driving the first docking seat and the second docking seat to move smoothly along the guide rod in the direction of approaching each other. When they move to the predetermined position, the first docking seat and the second docking seat are accurately inserted into the corresponding limit frame of the fuselage respectively. At this time, the locking hook mechanism is released, and the locking mechanism returns to the initial position under the action of the first stretching member, and extends into the limit hole of the fuselage limit frame, completes the locking, and realizes the stable connection between the wing and the body. When the wing and the body need to be disassembled, the locking hook mechanism is activated again, pulling the first stretching member and the second stretching member, and the locking mechanism withdraws from the limit hole and extends into the first docking seat and the second docking seat to release the locking of them. As the first docking seat and the second docking seat are completely removed from the limiting frame of the fuselage, the entire aircraft wing-body quick connection device can be easily disassembled from the aircraft, completing the disassembly process. Therefore, the present application can efficiently pull the first stretching member and the second stretching member through the rapid action of the locking hook mechanism, realize the extension and withdrawal of the locking mechanism, and the smooth movement of the first docking seat and the second docking seat, thereby reducing unnecessary installation space and shortening the connection and disassembly time of the wing-body. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the following is a brief introduction to the drawings required for use in the description of the embodiments of the present application. Obviously, the drawings described below are some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0017] Figure 1A schematic diagram of the structure of an aircraft wing-body quick connection device provided in an embodiment of the present application; Figure 2 A schematic diagram of the structure of the limit frame provided in the embodiment of the present application; Figure 3 A schematic diagram of the structure of the first docking seat and the second docking seat provided in an embodiment of the present application; Figure 4 for Figure 3 A cross-sectional view of BB in FIG. Figure 5 for Figure 4 A cross-sectional view of CC in FIG. Figure 6 for Figure 5 A cross-sectional view of DD in FIG. Figure 7 A schematic diagram of the structure of the guide rod provided in the embodiment of the present application; Figure 8 for Figure 3 A cross-sectional view of FF; Fig. 9 A schematic diagram of the structure of a spring latch provided in an embodiment of the present application; Fig.10 A schematic diagram of the structure of the locking hook mechanism provided in an embodiment of the present application; Fig.11 for Fig.10 A magnified image of point A; Fig.12 A schematic diagram of the structure of the pin holder provided in the embodiment of the present application; Fig.13 A schematic diagram of the structure of the lock cover provided in an embodiment of the present application; Fig.14 A schematic diagram of the structure of the limit seat provided in the embodiment of the present application; Fig.15 A schematic diagram of the structure of the fuselage and wing surface provided in an embodiment of the present application; Fig.16 A schematic diagram of the structure of the locking mechanism provided in an embodiment of the present application.

[0018] Icons: 1-first docking seat; 2-second docking seat; 3-locking hook mechanism; 31-first lock shell; 32-second lock shell; 33-limiting seat; 331-U-shaped structure; 34-pull buckle lock hook; 35-connecting rod; 36-lock cover; 361-spring latch; 37-pin seat; 4-second tensioning member; 5-first tensioning member; 51-rope; 52-reset elastic member; 53-baffle; 6-guide rod; 7-locking mechanism; 71-slider; 72-tension spring; 73-locking pin; 74-guide column; 8-limiting frame; 81-limiting hole; 9-support guide seat; 10-compression spring; 11-fuselage; 12-wing surface; 13-beam. DETAILED DESCRIPTION

[0019] The following will be combined with the drawings in the embodiments of the present application to clearly and completely describe the technical solutions in the embodiments of the present application. Obviously, the described embodiments are part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of this application.

[0020] In the description of the embodiments of the present application, it should be noted that the orientation or positional relationship indicated by the terms "center", "up", "down", "left", "right", "vertical", "horizontal", "inside", "outside", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the embodiments of the present application and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present application. The terms "first", "second", and "third" are used for descriptive purposes only and cannot be understood as indicating or implying relative importance. In addition, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be a connection between the two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the embodiments of the present application can be understood according to the specific circumstances.

[0021] The present application embodiment provides an aircraft wing-body quick connection device, such as Figures 1 to 16As shown. The aircraft wing-body quick connection device comprises a first docking seat 1, a second docking seat 2, a locking hook mechanism 3, a first stretching member 5, a second stretching member 4, at least one guide rod 6 and at least two locking mechanisms 7. The two ends of at least one guide rod 6 are respectively connected to adjacent beams 13 in the wing surface 12. The first docking seat 1 and the second docking seat 2 are respectively slidably connected to the two sides of the guide rod 6, and are located on the inner side of the adjacent beams 13 in the wing surface 12, and are configured to be inserted into the corresponding limit frame 8 of the fuselage 11. The first docking seat 1 and the second docking seat 2 are both provided with locking holes. One end of at least two locking mechanisms 7 passes through the corresponding locking holes and extends into the corresponding first docking seat 1 and the second docking seat 2. The limit frame 8 of the fuselage 11 is provided with a limit hole 81 corresponding to the locking hole. The two ends of the first stretching member 5 extend into the first docking seat 1 and the second docking seat 2 respectively, and are connected to the corresponding locking mechanism 7. The two ends of the second stretching member 4 are respectively connected to the first docking seat 1 and the second docking seat 2. The locking hook mechanism 3 is connected to the first stretching member 5 and the second stretching member 4, and is configured to pull the first stretching member 5 and the second stretching member 4 so that the first stretching member 5 drives the locking mechanism 7 located outside the locking hole to extend into the corresponding first docking seat 1 and the second docking seat 2, and at the same time, the second stretching member 4 drives the first docking seat 1 and the second docking seat 2 to move towards each other.

[0022] The wing surface 12 of the embodiment of the present application is a tail wing. In the present application, there are two guide rods 6, which are symmetrically arranged on both sides of the second stretching member 4. Similarly, there are two locking mechanisms 7.

[0023] It should be noted that when the wing-body needs to be connected, the lock hook mechanism 3 is started and starts to pull the first stretching member 5 and the second stretching member 4. As the first stretching member 5 moves, it drives the locking mechanism 7 originally located outside the locking hole to extend into the corresponding first docking seat 1 and the second docking seat 2. At the same time, the second stretching member 4 is pulled, driving the first docking seat 1 and the second docking seat 2 to move smoothly along the guide rod 6 in the direction of approaching each other. When they move to the predetermined position, the first docking seat 1 and the second docking seat 2 are respectively inserted into the corresponding limit frame 8 of the fuselage 11. At this time, the lock hook mechanism 3 is released, and the locking mechanism 7 returns to the initial position under the action of the first stretching member 5, and extends into the limit hole 81 of the limit frame 8 of the fuselage 11, completing the locking and realizing a stable connection between the wing-body. When the wing-body needs to be disassembled, the lock hook mechanism 3 is started again, pulling the first stretching member 5 and the second stretching member 4, and the locking mechanism 7 withdraws from the limit hole 81 and extends into the first docking seat 1 and the second docking seat 2 to release their lock. As the first docking seat 1 and the second docking seat 2 are completely removed from the limit frame 8 of the fuselage 11, the entire aircraft wing-body quick connection device can be easily disassembled from the aircraft, completing the disassembly process. Therefore, the present application can efficiently pull the first stretching member 5 and the second stretching member 4 through the rapid action of the locking hook mechanism 3, realize the extension and withdrawal of the locking mechanism 7, and the smooth movement of the first docking seat 1 and the second docking seat 2, thereby reducing unnecessary installation space and shortening the connection and disassembly time of the wing-body.

[0024] In the embodiment of the present application, the first tensioning member 5 includes a rope 51, two reset elastic members 52 and two baffles 53. The two reset elastic members 52 and the two baffles 53 are respectively located in the first docking seat 1 and the second docking seat 2. Both ends of the rope 51 extend into the first docking seat 1 and the second docking seat 2 respectively, and pass through the corresponding baffles 53 to be connected to the corresponding locking mechanism 7. One end of the two reset elastic members 52 is fixed to the side of the corresponding baffle 53 facing the locking mechanism 7, and the other end thereof is abutted against the corresponding locking mechanism 7.

[0025] It should be noted that the baffle 53 plays a role in guiding and fixing the resetting elastic member 52 , and the end surface of the resetting elastic member 52 away from the locking mechanism 7 must be firmly clamped to avoid loosening.

[0026] When the lock hook mechanism 3 pulls the rope 51, the two ends of the rope 51 will respectively drive the locking mechanism 7 in the first docking seat 1 and the second docking seat 2 to move toward the baffle 53. In this process, the pulling force of the rope 51 will be transmitted to the reset elastic member 52 through the locking mechanism 7, causing the reset elastic member 52 to be in a compressed state. When the rope 51 is not subjected to force, the reset elastic member 52 will use its elastic potential energy to push the locking mechanism 7 to return to the initial position.

[0027] In the embodiment of the present application, the aircraft wing-body quick connection device further includes two support guide seats 9. The two support guide seats 9 are respectively fixedly connected to the first docking seat 1 and the second docking seat 2, and are located on the side of the baffle 53 away from the locking mechanism 7. After the two ends of the rope 51 extend into the first docking seat 1 and the second docking seat 2 respectively, they bypass the corresponding support guide seats 9, and the support guide seats 9 are configured to guide the rope 51 to pass through the corresponding baffle 53.

[0028] It should be noted that the support guide seat 9 here plays an important guiding role in the turning of the rope 51, ensuring that the rope 51 can move along a predetermined path in the first docking seat 1 and the second docking seat 2, thereby improving the reliability and stability of the aircraft wing-body quick connection device.

[0029] In the embodiment of the present application, the locking mechanism 7 includes a slider 71, a tension spring 72 and two locking pins 73. The slider 71 and the tension spring 72 are both provided in the first docking seat 1 and the second docking seat 2. The two ends of the first tensile member 5 are respectively connected to the corresponding slider 71. The slider 71 is a hollow structure. The two ends of the tension spring 72 pass through the top wall and the bottom wall of the slider 71 respectively, and are connected to the two locking pins 73, and the two sides of the tension spring 72 abut against the top wall and the bottom wall of the slider 71. The longitudinal section of the slider 71 away from the first tensile member 5 is a triangular structure. The end portions of the two locking pins 73 away from the tension spring 72 extend out of the corresponding locking holes, and the two locking pins 73 close to the tension spring 72 are slidably connected to the top and bottom surfaces of the slider 71 away from the first tensile member 5.

[0030] Specifically, one end of the locking pin 73 close to the tension spring 72 is designed as an inclined surface, and the inclination of the inclined surface completely matches the inclination of the edge of the triangular structure of the slider 71. This design ensures that the locking pin 73 can slide more smoothly and stably along the inclined surface of the slider 71 when subjected to the tension of the tension spring 72, thereby achieving reliable locking and unlocking functions.

[0031] It should be noted that the slider 71 is designed as a hollow structure to accommodate the tension spring 72. The tension spring 72 is a double-hook design, with its two ends respectively hung on two locking pins 73, and the two sides of the tension spring 72 always keep in contact with the top wall and the bottom wall of the slider 71. Two locking holes are respectively provided on the first docking seat 1 and the second docking seat 2.

[0032] When the first tension member 5 is pulled, it drives the corresponding slider 71 to move in the first docking seat 1 or the second docking seat 2 in a direction away from the fuselage 11. Since the longitudinal section of the slider 71 away from the first tension member 5 is a triangular structure, the slider 71 can compress the tension spring 72 during the sliding process, thereby allowing the four locking pins 73 to extend into the corresponding locking holes. When the first tension member 5 is not pulled, the slider 71 will move toward the fuselage 11 under the action of the rebound force of the first tension member 5, and at this time, the tension spring 72 gradually returns to its initial state and drives the locking pin 73 back to the initial position.

[0033] In the embodiment of the present application, the locking mechanism 7 further includes a guide column 74. Two locking pins 73 are slidably connected to the two sides of the guide column 74. The tension spring 72 is sleeved on the outer wall of the guide column 74. The top surface and the bottom surface of the side of the slider 71 away from the first tension member 5 are both provided with a slide groove corresponding to the guide column 74.

[0034] It should be noted that the guide column 74 can ensure that the two locking pins 73 do not deviate when extending into or out of the locking hole, thereby ensuring the stability and reliability of the connection.

[0035] Specifically, in order to effectively prevent the locking pin 73 from rotating during operation, the cross section of the guide column 74 is designed to be non-circular, thereby limiting the rotational freedom of the locking pin 73 .

[0036] In the embodiment of the present application, the aircraft wing-body quick connection device further includes at least one compression spring 10. At least one compression spring 10 is disposed between the first docking seat 1 and the second docking seat 2, and is configured to limit the distance between the first docking seat 1 and the second docking seat 2 to ensure the stability and safety of the connection.

[0037] Specifically, the present embodiment uses two compression springs 10, which are symmetrically arranged on both sides of the second tension member 4 and located on the inner sides of the two guide rods 6. When the second tension member 4 is pulled, the first docking seat 1 and the second docking seat 2 will overcome the resistance generated by the compression springs 10 and move toward each other. However, due to the elastic force of the compression springs 10, the movement distance of the first docking seat 1 and the second docking seat 2 will be limited and will not move too much.

[0038] Furthermore, when the wing-body needs to be disassembled, the locking hook mechanism 3 will be activated again, pulling the first stretching member 5 and the second stretching member 4 at the same time. At this time, the locking mechanism 7 will withdraw from the limiting hole 81 and extend into the first docking seat 1 and the second docking seat 2, thereby releasing their locked state. As the first docking seat 1 and the second docking seat 2 are completely removed from the limiting frame 8 of the fuselage 11, the second stretching member 4 will return to its initial state. Under the action of the compression spring 10, the first docking seat 1 and the second docking seat 2 will move away from each other until they return to their initial positions.

[0039] In the embodiment of the present application, the lock hook mechanism 3 includes a first lock shell 31, a second lock shell 32, a limiting seat 33, a buckle lock hook 34 and a connecting rod 35. The first lock shell 31 is arranged on the skin of the fuselage 11. The second lock shell 32 is arranged on the skin of the wing surface 12 and corresponds to the first lock shell 31. The first lock shell 31 and the second lock shell 32 are located between the first docking seat 1 and the second docking seat 2. The limiting seat 33 is arranged on the first lock shell 31. A through hole is arranged on the side of the second lock shell 32 away from the first lock shell 31, and one end of the connecting rod 35 passes through the through hole. The connecting rod 35 is provided with connecting holes for the first tensile member 5 and the second tensile member 4 to pass through at intervals along its height direction. One end of the buckle lock hook 34 is rotatably connected to the side of the connecting rod 35 away from the connecting hole, and is configured to pull the connecting rod 35 to move when the angle with the second lock shell 32 is 90°. The other end of the buckle lock hook 34 is a free end, which is configured to be inserted into the limiting seat 33.

[0040] It should be noted that the operator first rotates the buckle hook 34 until the angle between it and the second lock shell 32 reaches 90°. Then, the operator continues to pull the free end of the buckle hook 34. In this process, the buckle hook 34 will pull the connecting rod 35 and the first tensile member 5 and the second tensile member 4 connected thereto to move together through the transmission effect of the connecting rod 35. When the first docking seat 1 and the second docking seat 2 are accurately inserted into the corresponding limit frames 8 of the fuselage 11 respectively, the operator releases the buckle hook 34. At this time, under the action of the rebound force of the first tensile member 5, the locking mechanism 7 will automatically return to the initial position, and the locking pin 73 will extend into the limit hole 81 of the limit frame 8 of the fuselage 11, thereby completing the locking action. Finally, the operator inserts the free end of the buckle hook 34 into the limit seat 33 to ensure that the lock hook mechanism 3 is in a stable locking state.

[0041] In the embodiment of the present application, the material of the buckle lock hook 34 is hard rubber. The limit seat 33 is a U-shaped structure 331, and the top opening width of the U-shaped structure 331 is smaller than the bottom opening width, so that after the buckle lock hook 34 is pressed into the limit seat 33, it can remain stable under any flight conditions and will not fall out due to vibration or external force. This self-locking mechanism enhances the reliability and safety of the buckle lock hook 34.

[0042] In the embodiment of the present application, the lock hook mechanism 3 further includes a lock cover 36. The lock cover 36 is hinged to one end of the second lock shell 32 away from the first lock shell 31, and a spring latch 361 is provided on the side of the lock cover 36 away from the second lock shell 32. A pin seat 37 corresponding to the spring latch 361 is provided on the side of the second lock shell 32 away from the first lock shell 31.

[0043] When the buckle lock hook 34 is pressed into the limiting seat 33 , the lock cover 36 is rotated to the first lock shell 31 , and the spring latch 361 is moved to be inserted into the pin seat 37 , so that the lock cover 36 is fixed.

[0044] In the embodiment of the present application, the longitudinal sections of the first docking seat 1 and the second docking seat 2 are both first trapezoidal structures. The longitudinal section of the limiting frame 8 of the fuselage 11 is a second trapezoidal structure corresponding to the first trapezoidal structure.

[0045] It should be noted that the second trapezoidal structure facilitates the insertion of the first docking socket 1 and the second docking socket 2 .

[0046] The various embodiments in this specification are described in a progressive manner, and the same or similar parts between the various embodiments can be referenced to each other. Each embodiment focuses on the differences from other embodiments.

[0047] The above embodiments are only used to illustrate the technical solutions of the present application, rather than to limit the present application. Although the present application has been described in detail with reference to the aforementioned embodiments, a person of ordinary skill in the art should understand that the technical solutions described in the aforementioned embodiments may still be modified, or some or all of the technical features thereof may be replaced by equivalents. However, these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the present application.

Claims

1. An aircraft wing-body quick connection device, characterized in that: It comprises a first docking seat (1), a second docking seat (2), a locking hook mechanism (3), a first stretching member (5), a second stretching member (4), at least one guide rod (6) and at least two locking mechanisms (7); Two ends of at least one of the guide rods (6) are respectively connected to adjacent beams (13) in the wing surface (12); The first docking seat (1) and the second docking seat (2) are respectively slidably connected to the two sides of the guide rod (6), and are located on the inner side of the adjacent beam (13) in the wing surface (12), and are configured to be inserted into the corresponding limit frame (8) of the fuselage (11); The first docking seat (1) and the second docking seat (2) are both provided with locking holes; One end of at least two of the locking mechanisms (7) passes through the corresponding locking holes and extends into the corresponding first docking seat (1) and the second docking seat (2); The limiting frame (8) of the fuselage (11) is provided with a limiting hole (81) corresponding to the locking hole; Two ends of the first stretching member (5) extend into the first docking seat (1) and the second docking seat (2) respectively, and are connected to the corresponding locking mechanism (7); Two ends of the second stretching member (4) are respectively connected to the first docking seat (1) and the second docking seat (2); The locking hook mechanism (3) is connected to the first stretching member (5) and the second stretching member (4), and is configured to pull the first stretching member (5) and the second stretching member (4), so that the first stretching member (5) drives the locking mechanism (7) located outside the locking hole to extend into the corresponding first docking seat (1) and the second docking seat (2), and at the same time, the second stretching member (4) drives the first docking seat (1) and the second docking seat (2) to move in a direction close to each other.

2. The aircraft wing-body quick connection device according to claim 1, characterized in that: The first tensioning member (5) comprises a rope (51), two resetting elastic members (52) and two baffles (53); The two resetting elastic members (52) and the two baffles (53) are respectively located in the first docking seat (1) and the second docking seat (2); Two ends of the rope (51) extend into the first docking seat (1) and the second docking seat (2) respectively, and pass through the corresponding baffle (53) to be connected to the corresponding locking mechanism (7); One end of each of the two resetting elastic members (52) is fixed to a side of the corresponding baffle (53) facing the locking mechanism (7), and the other end thereof abuts against the corresponding locking mechanism (7).

3. The aircraft wing-body quick connection device according to claim 2, characterized in that: It also includes two support guide seats (9); The two support guide seats (9) are respectively fixedly connected to the first docking seat (1) and the second docking seat (2), and are located on a side of the baffle (53) away from the locking mechanism (7); After the two ends of the rope (51) extend into the first docking seat (1) and the second docking seat (2), they bypass the corresponding support guide seat (9), and the support guide seat (9) is configured to guide the rope (51) to pass through the corresponding baffle (53).

4. The aircraft wing-body quick connection device according to claim 1, characterized in that: The locking mechanism (7) comprises a slider (71), a tension spring (72) and two locking pins (73); The first docking seat (1) and the second docking seat (2) are both provided with the sliding block (71) and the tension spring (72); Both ends of the first stretching member (5) are respectively connected to the corresponding sliding blocks (71); The slider (71) is a hollow structure; Two ends of the tension spring (72) respectively pass through the top wall and the bottom wall of the slider (71) and are connected to the two locking pins (73); two sides of the tension spring (72) abut against the top wall and the bottom wall of the slider (71); The longitudinal section of the sliding block (71) on the side away from the first stretching member (5) is a triangular structure; One end portion of the two locking pins (73) away from the tension spring (72) extends out of the corresponding locking hole, and the side of the two locking pins (73) close to the tension spring (72) is slidably connected to the top surface and bottom surface of the side of the slider (71) away from the first tension member (5).

5. The aircraft wing-body quick connection device according to claim 4, characterized in that: The locking mechanism (7) further comprises a guide column (74); The two locking pins (73) are slidably connected to two sides of the guide column (74); The tension spring (72) is sleeved on the outer wall of the guide column (74); The top surface and the bottom surface of the sliding block (71) on the side away from the first stretching member (5) are both provided with sliding grooves corresponding to the guide column (74).

6. The aircraft wing-body quick connection device according to claim 1, characterized in that: Also includes at least one compression spring (10); At least one of the compression springs (10) is arranged between the first docking seat (1) and the second docking seat (2), and is configured to limit the distance between the first docking seat (1) and the second docking seat (2).

7. The aircraft wing-body quick connection device according to claim 1, characterized in that: The lock hook mechanism (3) comprises a first lock housing (31), a second lock housing (32), a limit seat (33), a buckle lock hook (34) and a connecting rod (35); The first lock housing (31) is arranged on the skin of the fuselage (11); The second lock housing (32) is arranged on the skin of the wing surface (12) and corresponds to the first lock housing (31); The first lock housing (31) and the second lock housing (32) are located between the first docking seat (1) and the second docking seat (2); The limiting seat (33) is arranged on the first lock housing (31); A through hole is provided on a side of the second lock housing (32) away from the first lock housing (31), and one end of the connecting rod (35) passes through the through hole; The connecting rod (35) is provided with connection holes for the first tensile member (5) and the second tensile member (4) to pass through at intervals along its height direction; One end of the drawstring lock hook (34) is rotatably connected to a side of the connecting rod (35) away from the connecting hole, and is configured to pull the connecting rod (35) to move when the angle between the drawstring lock hook (34) and the second lock shell (32) is 90°; the other end of the drawstring lock hook (34) is a free end, and is configured to be inserted into the limit seat (33).

8. The aircraft wing-body quick connection device according to claim 7, characterized in that: The material of the buckle lock hook (34) is hard rubber; The limiting seat (33) is a U-shaped structure (331), and the width of the top opening of the U-shaped structure (331) is smaller than the width of the bottom opening thereof.

9. The aircraft wing-body quick connection device according to claim 7, characterized in that: The locking hook mechanism (3) further comprises a locking cover (36); The lock cover (36) is hinged to one end of the second lock housing (32) away from the first lock housing (31), and a spring latch (361) is provided on one side of the lock cover (36) away from the second lock housing (32); A pin seat (37) corresponding to the spring latch (361) is provided on a side of the second lock housing (32) away from the first lock housing (31).

10. The aircraft wing-body quick connection device according to claim 1, characterized in that: The longitudinal cross-sections of the first docking seat (1) and the second docking seat (2) are both first trapezoidal structures; The longitudinal section of the limiting frame (8) of the fuselage (11) is a second trapezoidal structure corresponding to the first trapezoidal structure.

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